Aircraft collision avoidance system

ABSTRACT

An aircraft collision avoidance system including (a) at least one separation monitoring device connectable to at least a portion of an aircraft and/or vehicle, the separation monitoring device comprising (1) at least one transmitter, (2) at least one receiver, and (3) an image sensor, and (b) a master unit.

CROSS-REFERENCE TO RELATED APPLICATION(S)

This application is a continuation-in-part of U.S. application Ser. No.14/457,040, filed Aug. 11, 2014, entitled “Aircraft collision avoidancesystem” which is a continuation of U.S. application Ser. No. 13/608,678,filed Sep. 10, 2012, now U.S. Pat. No. 8,803,710, entitled “Aircraftcollision avoidance system” which is a continuation of U.S. applicationSer. No. 12/396,015, filed Mar. 2, 2009, now U.S. Pat. No. 8,264,377,entitled “Aircraft collision avoidance system”—all of which are herebyincorporated herein by reference in their entirety, including allreferences cited therein.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates in general to aircraft collision avoidancesystems and, more particularly, to an aircraft collision avoidancesystem which is designed to minimize and/or eliminate damage to anaircraft during ground transportation of the same to and/or from, forexample, a hangar or other facility.

2. Background Art

Collision avoidance systems have been known in the aviation industry foryears. While collision avoidance systems have been known in the art,issues relative to system portability and multi-aircraft usabilityremain largely problematic.

Aircraft are typically stored in hangars or outside along otheraircraft. A common problem in transporting aircraft from a hangar to thetarmac, and vice-versa, is a phenomenon known as “hangar rash.” Hangarrash is caused by improper ground handling of an aircraft and commonlyoccurs when the aircraft is being pushed or pulled from the hanger by avehicle, such as a tractor. An inattentive or careless tractor operatormay inadvertently cause a wing, horizontal stabilizer, and/or verticalstabilizer of the aircraft to contact, for example, another aircraft, ahanger wall, and/or a hanger door—causing extremely expensive andpotentially catastrophic damage to the aircraft.

Some aircraft are provided with collision warning devices fabricatedinto the wings, stabilizers and/or nose cones of the aircraft. Thesedevices suffer from numerous drawbacks including, but not limited to,the fact that the devices are integral instruments of the aircraft.Typically, this means that an individual operating the collision warningdevice must possess required FAA certifications which are necessary tolegally operate the plane itself in order to operate the collisionwarning devices.

Thus the need exists for an aircraft collision avoidance system, whichis portable and facilitates rapid installation, removal, and use of thecollision avoidance system toward multi-aircraft utilization andavoidance of strict FAA certifications associated with collisionavoidance systems which are fully integrated into an aircraft.

SUMMARY OF THE INVENTION

In one embodiment the present invention is directed to an aircraftcollision avoidance system comprising: (a) at least one separationmonitoring device connectable to at least a portion of an aircraft, theseparation monitoring device comprising: (1) at least one transmittercapable of selectively transmitting signals which are reflected off ofan object and received by at least one receiver, the reflected signalsdefining a separation distance between the at least one receiver and theobject and wherein the at least one transmitter outputs a separationdistance signal representative of the separation distance; and (2) anoptional image sensor preferably in communication with a master unit;and (b) a master unit for receiving and analyzing the separationdistance signals output by the at least one transmitter and outputting awarning signal to a warning device when the at least one separationmonitoring device is within a predetermined distance from the object.

In another embodiment the present invention is directed to an aircraftcollision avoidance system, comprising: (a) at least one wirelesstransceiver capable of selectively transmitting signals and receivingsignals which are reflected back to the wireless transceiver off of anobject in order to define a separation distance between the wirelesstransceiver and the object and wherein the wireless transceiver outputsa separation distance signal representative of the separation distance;and (b) a master unit for receiving and analyzing the separationdistance signals output by the wireless transceiver, the master unitoutputting a warning signal to a warning device when the wirelesstransceiver is within a predetermined distance from an object.

In yet another embodiment, a separation monitoring device is disposed onat least one of a wing and a horizontal stabilizer of an aircraft andthe master unit communicates with the separation monitoring device tomonitor the position of at least one of the wing and the horizontalstabilizer of the aircraft relative to an object.

In a preferred embodiment the at least one separation monitoring deviceis connected to at least a portion of at least one of a wing and ahorizontal stabilizer of an aircraft, wherein the at least oneseparation monitoring device transmits signals in an arcuate patternboth horizontally and substantially co-planar to at least one of thewing and the horizontal stabilizer and receives signals reflected off ofan object and outputs a separation distance signal representing theseparation distance between the object and the at least one separationmonitoring device.

In another embodiment, the at least one separation monitoring device isconnected to at least a portion of at least one of a wing and ahorizontal stabilizer of an aircraft, wherein the at least oneseparation monitoring device transmits and receives signals bothvertically and substantially perpendicularly to at least one of the wingand the horizontal stabilizer and outputs a separation distance signal.

In accordance with the present invention, each wing, each horizontalstabilizer, each vertical stabilizer, at least a portion of a fuselageof an aircraft, and/or a tug/vehicle comprise at least one separationmonitoring device.

In yet another embodiment, when at least one of the wings of theaircraft are within a predetermined distance away from an object, themaster unit communicates a warning to an individual so as to preventcollisions between at least one of the wings of the aircraft and anobject.

In one embodiment of the present invention the warning device comprisesa speaker capable of communicating an audible warning when the warningdevice receives warning signals from the master unit.

In yet another embodiment, when the separation distance between theseparation monitoring device and the object decreases the audiblewarning increases in decibel level.

In another embodiment, the warning device of the master unit comprises avisual display communicating a visible warning.

In accordance with the present invention, the visual display comprises aplurality of light emitting diodes which are illuminated when the masterunit communicates a warning signal to the warning device.

In a preferred embodiment, the master unit is in electricalcommunication with a vehicle utilized to translate the aircraft.

In yet another embodiment, when the at least one transceiver is within acollision distance the master unit automatically stops the vehicle.

In another embodiment, the master unit comprises a communicator deviceselected from the group consisting of: a personal digital assistant, acellular telephone, or a global positioning device.

In accordance with the present invention, the at least one separationmonitoring device and the master unit communicate wirelessly via atleast one wireless communication protocol, wherein the at least onecommunication protocol is selected from the group consisting of:infrared, bluetooth, radio frequencies or Wi-Fi.

In one embodiment, the present invention is directed to an aircraftcollision avoidance system for monitoring the position of at least aportion of an aircraft relative to an object, the system comprising: (a)at least one separation monitoring device connected to at least aportion the aircraft, the separation monitoring device comprising: (1)at least one transceiver, the transceiver capable of transmittingsignals and receiving signals which are reflected back to thetransceiver off of at least a portion of the object to define aseparation distance and wherein the at least one transceiver wirelesslyoutputs a separation distance signal; and (b) a master unit forreceiving and analyzing the separation distance signals output by the atleast one transceiver and outputting a warning signal to a warningdevice when the at least one transceiver is within a predetermineddistance from the object.

In another embodiment of the present invention, the object is a door ofa hangar.

In yet another embodiment of the present invention, the object isanother aircraft.

In accordance with the present invention, each wing and each horizontalstabilizer and at least a portion of a fuselage of an aircraft compriseat least one separation monitoring device.

In yet another embodiment, the master unit is electrical communicationwith a vehicle utilized to move or displace the aircraft.

In accordance with the present invention, when the at least onetransceiver is within a collision distance the master unit automaticallystops the vehicle.

BRIEF DESCRIPTION OF THE DRAWINGS

Certain embodiments of the present invention are illustrated by theaccompanying figures. It will be understood that the figures are notnecessarily to scale and that details not necessary for an understandingof the invention or that render other details difficult to perceive maybe omitted. It will be understood that the invention is not necessarilylimited to the particular embodiments illustrated herein.

The invention will now be described with reference to the drawingswherein:

FIG. 1 of the drawings is top plan view of an aircraft disposed within ahangar, the aircraft having a plurality of separation monitoringdevices, in accordance with the present invention;

FIG. 2 of the drawings is schematic representation of an aircraftcollision avoidance system, in accordance with the present invention;

FIG. 3 of the drawings is schematic representation of an alternateembodiment of an aircraft collision avoidance system, in accordance withthe present invention;

FIG. 4 of the drawings is a perspective view of a separation monitoringdevice of an aircraft collision avoidance system, in accordance with thepresent invention; and

FIG. 5 of the drawings is a perspective view of a master unit of anaircraft collision avoidance system, in accordance with the presentinvention.

DETAILED DESCRIPTION OF THE INVENTION

While this invention is susceptible of embodiment in many differentforms, there is shown in the drawings and will herein be described indetail several specific embodiments with the understanding that thepresent disclosure is to be considered as an exemplification of theprinciples of the invention and is not intended to limit the inventionto the embodiments illustrated.

It will be understood that like or analogous elements and/or components,referred to herein, may be identified throughout the drawings with likereference characters.

Referring now to the drawings and to FIGS. 1 and 2 collectively, anaircraft collision avoidance system 10 is shown in association with anaircraft 14 located in a hangar 18. Generally, the arrows shown in FIGS.1 and 2 represent the direction of signal transmission although somedevices may be capable of two-way communication. More specifically, theaircraft collision avoidance system 10 comprises at least one separationmonitoring device 22 and a master unit 26. The separation monitoringdevice or distance measuring sensor 22 comprises at least onetransmitter 30 which is capable of transmitting a signal 34 (e.g. anultrasonic signal). When the signal 34 is reflected off of an object,for example, a hangar door 38, the signal 34 is then received by areceiver 42. The signal 34 may be transmitted in a substantially arcuatepattern covering an arc having an angle of θ degrees. The angle of θdegrees may preferably cover an area, which is at least as wide as theterminal end 32 of the wing 36 of the aircraft 14. The distance betweenthe hangar door 38 and the receiver 42 is known as a separation distance46. The transmitter 30 then outputs a separation distance signal 50 thatincludes data representative of the separation distance 46.

It will be understood that the separation monitoring device 22 maycomprise a plurality of transmitters 30 and receivers 42 to cover alarger area. Furthermore, the separation monitoring device may comprisea plurality of transmitters 30 and/or receivers 42 that cooperativelyvalidate a signal to minimize and/or avoid false positive and/ornegative indications. The separation monitoring device 22 preferablycomprises a housing 44 for enclosing the aforementioned parts 30 and 42.The housing 44 is preferably fabricated from any one of a number ofmaterials, including, but not limited to, a resin and/or polymer, ametal or alloy, a fiberglass material, a natural product such as wood,or any combinations thereof. The separation monitoring device 22 alsopreferably comprises a releasable securement member 47 (see FIG. 4) forconnecting the housing 44 to at least a portion of an aircraft 14 and/orvehicle 110. The releasable securement member 47 may include, forexample, a suction cup (e.g., ram suction cup mount), or a removableadhesive disposed between the housing 44 and the aircraft 14.

The separation monitoring device 22 further comprises a microprocessor54 for controlling the transmitter 30 and receiver 42 and an energystorage device 58 (e.g. a primary and/or secondary battery). The energystorage device 58 provides electrical energy to the separationmonitoring device 22.

In accordance with the present invention, the separation monitoringdevice 22 may be non-integrated (e.g., separate and/or removable) fromthe aircraft 14 and/or the vehicle 110, or, alternatively, theseparation monitoring device 22 may be integrated (e.g., built in yetremovable and/or non-removable) from the aircraft 14 and/or the vehicle110.

In one embodiment of the present invention, the separation monitoringdevice 22 further comprises an image sensor for providing a user with animage (e.g., a photo, a video) associated with one or more separationmonitoring devices. Examples of suitable image sensors include videocamera tubes, semiconductor charge-coupled devices (CCD), active pixelsensor in complementary metal-oxide-semiconductors (CMOS), N-typemetal-oxide-semiconductors (NMOS, Live MOS), and back-side illuminatedcomplementary metal-oxide-semiconductors (BSI-CMOS).

It will be understood that the above-identified image sensors arecommercially available from a plurality of sources, including Agilent,Aptina, Canesta, Canon, Caeleste, CMOSIS, Dalsa, Eastman Kodak, ESSTechnology, Fujifilm, MagnaChip, Matsushita, MAZeT GmbH, Mitsubishi,Nikon OmniVision Technologies, ON Semiconductor, Cypress Semiconductor,PixArt Imaging, Pixim, Samsung, Sharp, Sony, STMicroelectronics,Toshiba, TowerJazz, Town Line Technologies, TransChip, Trusight andTrusense Imaging—just to name a few suppliers.

Additional examples of suitable image sensors for use in accordance withthe present invention include U.S. Pat. No. 6,359,323 B1 entitled “Colorimage sensor and method for fabricating the same,” United States PatentApplication Publication No. 2006/0043261 A1 entitled “Solid state imagepickup device and image pickup system comprising it,” U.S. Pat. No.7,129,979 B1 entitled “Image sensor pixel for global electronicshuttering,” United States Patent Application Publication No.2004/0147059 A1 entitled “Method for manufacturing CMOS image sensorhaving microlens therein with high photosensitivity,” U.S. Pat. No.5,990,506 A entitled “Active pixel sensors with substantially planarizedcolor filtering elements,” U.S. Pat. No. 6,235,549 B1 entitled “Methodand apparatus for employing a light shield to modulate pixel colorresponsivity,” U.S. Pat. No. 6,765,276 B2 entitled “Bottomantireflection coating color filter process for fabricating solid stateimage sensors,” U.S. Pat. No. 6,486,913 B1 entitled “Pixel array withshared reset circuitry,” U.S. Pat. No. 6,872,584 B2 entitled “Solidstate image sensor and method for fabricating the same,” United StatesPatent Application Publication No. 2006/0011813 A1 entitled “Imagesensor having a passivation layer exposing at least a main pixel arrayregion and methods of fabricating the same,” United States PatentApplication Publication No. 2007/0187793 A1 entitled “Filter, colorfilter array, method of manufacturing the color filter array, and imagesensor,” U.S. Pat. No. 6,379,992 B2 entitled “Method for fabricating animage sensor,” United States Patent Application Publication No.2006/0138500 A1 entitled “CMOS image sensor and method for fabricatingthe same,” United States Patent Application Publication No. 2005/0263839A1 entitled “Photoelectric converting film stack type solid-state imagepickup device, and method of producing the same,” United States PatentApplication Publication No. 2007/0090274 A1 entitled “Image sensorsincluding active pixel sensor arrays,” United States Patent ApplicationPublication No. 2006/0157761 A1 entitled “Image sensor withself-boosting and methods of operating and fabricating the same,” U.S.Pat. No. 6,369,417 B1 entitled “CMOS image sensor and method forfabricating the same,” U.S. Pat. No. 6,127,668 A entitled “Solid stateimage pickup device and method for manufacturing the same,” UnitedStates Patent Application Publication No. 2007/0023802 A1 entitled “CMOSimage sensor and method of fabricating the same,” United States PatentApplication Publication No. 2005/0090035 A1 entitled “Method forfabricating CMOS image sensor protecting low temperature oxidedelamination,” and United States Patent Application Publication No.2006/0261342 A1 entitled “Imaging device having a pixel cell with atransparent conductive interconnect line and the method of making thepixel cell”—all of which are hereby incorporated herein by reference intheir entirety, including all references cited therein.

In another embodiment of the present invention, the separationmonitoring device 22 further comprises a microwave and/or radartransmitter and receiver, in addition to, or in replacement of a soundwave transmitter (e.g., ultrasonic). It will be understood that such atransmitter may be configured in a manner consistent with U.S. Pat. No.3,733,604 entitled “A Aircraft guidance system,” U.S. Pat. No. 3,739,379A entitled “Coherent pulse doppler altimeter,” U.S. Pat. No. 3,579,238 Aentitled “Automatic power control of a pulse modulator,” German PatentNo. DE 2,312,145 A1 entitled “Method and apparatus for distancemeasurement using microwaves,” U.S. Pat. No. 4,044,354 A entitled“Distance measurement using microwaves,” U.S. Pat. No. 3,985,030 Aentitled “Ultrasonic acoustic pulse echo ranging system,” U.S. Pat. No.4,336,538 A entitled “Radar systems,” U.S. Pat. No. 4,319,246 A entitled“Radar systems,” U.S. Pat. No. 4,225,866 A entitled “Automaticfailure-resistant radar transmitter,” U.S. Pat. No. 4,805,453 A entitled“Tank sonic gauging system and methods,” U.S. Pat. No. 4,727,311 Aentitled “Microwave moisture measurement using two microwave signals ofdifferent frequency and phase shift determination,” U.S. Pat. No.6,130,636 A entitled “Continuous wave radar system,” U.S. Pat. No.5,898,401 A entitled “Continuous wave radar altimeter,” and U.S. Pat.No. 4,758,839 A entitled “Terrain profile radar system”—all of which arehereby incorporated herein by reference in their entirety, including allreferences cited therein.

In one embodiment of the present invention, the master unit 26 is incommunication with the image sensor. In particular, the master unit 26preferably displays the image provided by the image sensor using, forexample a passive matrix and/or active matrix display.

The master unit 26 generally comprises a receiver 62, a computer unit66, a warning device 70 and an energy storage device 74. The master unitpreferably comprises a housing 72 for enclosing the aforementioned parts62, 66, 70 and 74. The housing 72 is preferably fabricated from any oneof a number of materials, including, but not limited to a resin and/orpolymer, a metal or alloy, a fiberglass material, a natural product suchas wood, or any combinations thereof.

The receiver 62 is preferably provided to receive separation distancesignals 50 communicated by the transmitter 30 of the separationmonitoring device 22 and communicate the separation distance signals 50to the computer unit 66. The computer unit 66 is shown as preferablycomprising the same components as a typical computer, for example, amemory 78 and a processing unit 82. The computer unit 66 is programmedto analyze the separation distance signals 50 and compare them to atleast one of a predetermined distance and a collision distance storedwithin the memory 78 of the computer unit 66. When the computer unit 66determines that the separation monitoring device 22 is within thepredetermined distance, the computer unit 66 communicates a warningsignal 94 to the warning device 70. The predetermined distance may beselectable by utilizing an optional interface 80 located on the masterunit 26. Also, the predetermined distance and collision distances may behard coded into the master unit 26 and stored in the memory 78. By wayof non-limiting example, the predetermined distance may include distanceof, for example, one meter. When the separation monitoring device 22 iswithin one meter of the hangar door 38 or any other object, the masterunit outputs a warning signal 94 to the warning device 70. It will beunderstood that the predetermined distance may include, for example, onemeter, although any distance or range of distances may be utilized. Thecollision distance is preferably defined as a distance at which there isa material possibility of a collision, such as, for example, six inches.When the computer unit 66 determines that the separation monitoringdevice 22 is within the collision distance, the computer unit 66communicates a collision signal 98 to the warning device 70.

The warning device 70 comprises, for example an audio device whichpreferably comprises a speaker 102 (see FIG. 5) that communicates anaudible warning at a sufficient frequency and decibel level so as toalert an individual of an impending collision. Also, the warning device70 may communicate an increasing or decreasing audible warning dependingon the separation distance 46 that is communicated to the master unit26. For example, as the separation distance 46 decreases, the volume ofthe audio warning from the warning device 70 will preferably increase indecibel level.

The warning device 70 may also preferably comprise a visual display 106comprising a plurality of light emitting diodes that illuminate to alertan individual of an impending collision. The greater the number of lightemitting diodes that are illuminated, the greater the risk of acollision. Other visual displays may include, but are not limited to, aclosed circuit video display. Also, as with the separation monitoringdevice 22, to power all the constituent parts of the master unit 26, theenergy storage device 98, for example, a battery, communicateselectrical energy to the master unit 26.

In another embodiment of the present invention, the separationmonitoring device 22 may comprise a transceiver 106 (see FIG. 3) orplurality of transceivers which both transmit and receive signals andoutput separation distance signals 50 representative of the separationdistance 46 between, for example, the hangar door 38 and the separationmonitoring device 22.

The master unit 26 may be connectable, either electrically and/ormechanically to a vehicle 110 and at least partially control the vehicle110. The vehicle 110 is preferably used to push and/or pull the aircraft14 out of the hanger 18. When the separation monitoring device 22disposed on at least a portion of the aircraft 14 is within thecollision distance, the warning device 70 communicates a stop signal tothe vehicle 110 which causes the vehicle 110 to stop.

The master unit 26 may comprise, for example, a handheld unit, apersonal digital assistant, a cellular telephone, and/or a laptopcomputer—although anyone of a number of types of communication devicescapable of receiving signals from the separation monitoring device 22and communicating a warning to an operator of the vehicle 110 that wouldbe known to one of ordinary skill in the art with the present disclosurebefore them are likewise contemplated for use with the presentinvention. It will be understood that the master unit 26 may befabricated as an integral part of the vehicle 110.

The master unit 26 may preferably communicate with the at least oneseparation monitoring device 22 via the receiver 62 over a variety ofdifferent wireless communication protocols, for example, Wi-Fi signals(e.g., 802.11n, 802.11b, 802.11g, etcetera), infrared signals, bluetoothsignals, radio frequencies (e.g., 900 Mhz, 1.8 GHz, 2.4 GHz, etcetera)or combinations thereof.

If the separation monitoring device 22 communicates infrared signals,the receiver 62 of the master unit 26 should preferably comprise aninfrared sensor. Likewise, if the separation monitoring device 22communicates Bluetooth signals, the receiver 62 of the master unit 26should preferably comprise a Bluetooth sensor. Furthermore, if theseparation monitoring device 22 communicates radio frequency signals,the receiver 62 of the master unit 26 should preferably comprise a radiofrequency antenna. Lastly, if the separation monitoring device 22communicates Wi-Fi signals, the receiver 62 of the master unit 26 shouldpreferably comprise a Wi-Fi antenna.

In operation, the plane 14 is provided with a plurality of separationmonitoring devices 22. For example, in one embodiment, seven separationmonitoring devices 22 are positioned on the aircraft (e.g., forwardfacing on the left wing, forward facing on the right wing, rearwardfacing on the left wing, rearward facing on the right wing, rearwardfacing on the vertical stabilizer, rearward facing on the lefthorizontal stabilizer, and rearward facing on the right horizontalstabilizer, etcetera) and one separation monitoring device 22 ispositioned on the back of the vehicle or tug. In particular, each of theterminal ends 32 of the wings 36 of the aircraft 14 preferably compriseseparation monitoring devices 22 connected thereto. Also, the terminalends 126 of the horizontal stabilizers 130 preferably compriseseparation monitoring devices 22 connected thereto. The separationmonitoring devices 22 communicate signals 34 horizontally andsubstantially co-planar to the wings 36 and horizontal stabilizers 130,respectively. The signals 134 may be transmitted in an arcuate patterncovering an arc having an angle of θ degrees. The angle of θ degrees maypreferably cover an area that is at least as wide as the terminal ends32 of the wings 36 and the terminal ends 126 of the horizontalstabilizers 130 of the aircraft 14. The signals 34 reflect off of thehangar door 38 back towards the separation monitoring device 22 thattransmitted the signal. If one of the separation monitoring devices 22communicates a separation distance signal 50 that is analyzed by themaster unit 26 and determined to be within the predetermined distancefrom the hangar door 38, the separation monitoring device 22communicates a warning signal 94 to the master unit 26 associated withthe vehicle 110. The master unit 26 displays a visual and/or audiblewarning to the operator of the vehicle 110 notifying them that theaircraft 14 is too close to the hangar door 38. If the operator ignoresthe visual and/or audible warning, and one of the separation monitoringdevices 22 communicates a separation distance signal 50 that is analyzedby the master unit and determined to be within the collision distance,the master unit 26 sends an electrical signal to the vehicle 110 thatpreferably stops the vehicle 110.

The foregoing description merely explains and illustrates the inventionand the invention is not limited thereto except insofar as the appendedclaims are so limited, as those skilled in the art who have thedisclosure before them will be able to make modifications withoutdeparting from the scope of the invention.

What is claimed and desired to be secured by Letters Patent of theUnited States is:
 1. An aircraft collision avoidance system, comprising:at least one separation monitoring device connectable to at least aportion of an aircraft, the separation monitoring device comprising: atleast one transmitter capable of selectively transmitting signals whichare reflected off of an object and received by at least one receiver,the reflected signals defining a separation distance between the atleast one receiver and the object and wherein the at least onetransmitter outputs a separation distance signal representative of theseparation distance; and an image sensor; and a master unit forreceiving and analyzing the separation distance signals output by the atleast one transmitter and outputting a warning signal to a warningdevice when the at least one separation monitoring device is within apredetermined distance from the object, and wherein the master unit isin communication with the image sensor.
 2. An aircraft collisionavoidance system, comprising: at least one wireless transceiver capableof selectively transmitting signals and receiving signals which arereflected back to the wireless transceiver off of an object in order todefine a separation distance between the wireless transceiver and theobject and wherein the wireless transceiver outputs a separationdistance signal representative of the separation distance; and an imagesensor; and a master unit for receiving and analyzing the separationdistance signals output by the wireless transceiver, the master unitoutputting a warning signal to a warning device when the wirelesstransceiver is within a predetermined distance from an object, andwherein the master unit is in communication with the image sensor. 3.The aircraft collision avoidance system according to claim 1, wherein aseparation monitoring device is disposed on at least one of a wing and ahorizontal stabilizer of an aircraft and the master unit communicateswith the separation monitoring device to monitor the position of atleast one of the wing and the horizontal stabilizer of the aircraftrelative to an object.
 4. The aircraft collision avoidance systemaccording to claim 1, wherein the at least one separation monitoringdevice is connected to at least a portion of at least one of a wing anda horizontal stabilizer of an aircraft, wherein the at least oneseparation monitoring device transmits signals in an arcuate patternboth horizontally and substantially co-planar to at least one of thewing and the horizontal stabilizer and receives signals reflected off ofan object and outputs a separation distance signal representing theseparation distance between the object and the at least one separationmonitoring device.
 5. The aircraft collision avoidance system accordingto claim 1, wherein the at least one separation monitoring device isconnected to at least a portion of at least one of a wing and ahorizontal stabilizer of an aircraft, wherein the at least oneseparation monitoring device transmits and receives signals bothvertically and substantially perpendicularly to at least one of the wingand the horizontal stabilizer and outputs a separation distance signal.6. The aircraft collision avoidance system according to claim 1, whereineach wing, each horizontal stabilizer and at least a portion of afuselage of an aircraft comprise at least one separation monitoringdevice.
 7. The aircraft collision avoidance system according to claim 6,wherein when at least one of the wings of the aircraft are within apredetermined distance away from an object, the master unit communicatesa warning to an individual so as to prevent collisions between at leastone of the wings of the aircraft and an object.
 8. The aircraftcollision avoidance system according to claim 1, wherein the warningdevice comprises a speaker capable of communicating an audible warningwhen the warning device receives warning signals from the master unit.9. The aircraft collision avoidance system according to claim 8, whereinwhen the separation distance between the separation monitoring deviceand the object decreases the audible warning increases in decibel level.10. The aircraft collision avoidance system according to claim 1,wherein the warning device of the master unit comprises a visual displaycommunicating a visible warning.
 11. The aircraft collision avoidancesystem according to claim 10, wherein the visual display comprises aplurality of light emitting diodes which are illuminated when the masterunit communicates a warning signal to the warning device.
 12. Theaircraft collision avoidance system according to claim 1, wherein themaster unit is in electrical communication with a vehicle utilized totranslate the aircraft.
 13. The aircraft collision avoidance systemaccording to claim 12, wherein when the at least one separationmonitoring device is within a collision distance the master unitautomatically stops the vehicle.
 14. The aircraft collision avoidancesystem according to claim 1, wherein the master unit comprises acommunicator device selected from the group consisting of: a personaldigital assistant, a cellular telephone, a laptop, or a globalpositioning device.
 15. The aircraft collision avoidance systemaccording to claim 1, wherein the at least one separation monitoringdevice and the master unit communicate wirelessly via at least onewireless communication protocol, wherein the at least one communicationprotocol is selected from the group consisting of: Infrared, Bluetooth,Radio Frequencies or Wi-Fi.
 16. An aircraft collision avoidance system,comprising: at least one separation monitoring device connectable to atleast a portion of an aircraft, the separation monitoring devicecomprising: at least one sound transmitter capable of selectivelytransmitting signals which are reflected off of an object and receivedby at least one receiver, the reflected signals defining a separationdistance between the at least one receiver and the object and whereinthe at least one transmitter outputs a separation distance signalrepresentative of the separation distance; at least one radartransmitter capable of selectively transmitting radar signals which arereflected off of an object and received by at least one receiver, thereflected signals defining a separation distance between the at leastone receiver and the object and wherein the at least one transmitteroutputs a separation distance signal representative of the separationdistance; an image sensor; and a master unit for receiving and analyzingthe separation distance signals output by the at least one soundtransmitter and outputting a warning signal to a warning device when theat least one separation monitoring device is within a predetermineddistance from the object, and wherein the master unit is incommunication with the image sensor.